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首页> 外文会议>Proceedings of the 7th European symposium on aerothermodynamics. >DESIGN OF A SCRAMJET NOZZLE WITH STREAMLINE TRACING TECHNIQUE AND REFERENCE TEMPERATURE METHODE
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DESIGN OF A SCRAMJET NOZZLE WITH STREAMLINE TRACING TECHNIQUE AND REFERENCE TEMPERATURE METHODE

机译：基于流线跟踪技术和参考温度方法的胶卷喷嘴设计

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摘要

This study presents a method to find an optimal shapernof a three-dimensional supersonic nozzle for arnrectangular scramjet combustion chamber with roundedrnedges by taking into account the skin friction effects.rnThe geometric and flow constraints are defined withinrnthe German DFG GRK 1095/2 project and therndesigned nozzle will be part of a scramjet demonstratorrnconfiguration [1]. The nozzle inlet conditions are meanrnvalues of the combustion chamber exit conditions withrnthe assumption of a constant specific heat ratio. Torngenerate the shape of the nozzle a streamline tracingrntechnique is applied to an axis-symmetric flow fieldrncalculated by the Method of Characteristics (MOC).rnSkin friction in relatively high pressure supersonic flowrnfrom the combustion chamber is very dominant andrncannot be neglected in the design process. Thereforernthe skin friction is calculated using the ReferencernTemperature Method (RTM) and used for therndetermination of the thrust and moment vectors. Thisrnallows considering viscous effects without boundaryrnlayer calculations. With this approach an optimalrntruncated ideal nozzle contour which yields therngeometric constraints can be derived. For the validationrnof this method comparative calculations have beenrncarried out with the DLR code TAU on an exemplaryrnaxis-symmetric supersonic nozzle for different flowrnconditions. Results showed a good agreement. Finallyrnfor the three-dimensional nozzle the analytical solutionrnfor the inviscous and viscous case provided comparablerndata like TAU simulations. Further simplifications ofrnthe approach for an efficient three-dimensional nozzlerndesign will be addressed in the paper.
机译：这项研究提出了一种方法，该方法考虑了蒙皮摩擦效应，为带有圆角边缘的矩形矩形超燃冲压燃烧室寻找最佳形状的三维超声速喷嘴。在德国DFG GRK 1095/2项目和设计的喷嘴中定义了几何和流量约束将成为超燃冲压发动机演示装置的一部分[1]。喷嘴入口条件是假设恒定比热比的燃烧室出口条件的平均值。扭转喷嘴的形状，将流线描图技术应用于通过特征方法（MOC）计算的轴对称流场。在来自燃烧室的相对高压超音速流中，皮肤摩擦非常占主导地位，并且在设计过程中不可忽略。因此，皮肤摩擦是使用参考温度法（RTM）计算的，并用于推力和力矩矢量的确定。这使得无需边界层计算即可考虑粘性效应。通过这种方法，可以得出产生几何约束的最佳截断的理想喷嘴轮廓。为了验证该方法，已经针对不同的流动条件在示例性的轴对称超音速喷嘴上用DLR代码TAU进行了比较计算。结果显示出良好的一致性。最后，对于三维喷嘴，粘性和粘性情况的解析解提供了类似TAU模拟的数据。本文将讨论有效的三维喷嘴设计方法的进一步简化。

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  • 会议地点 Brugge(BE)
  • 作者

    J. Riehmer; A. Gülhan;

  • 作者单位

    German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, Supersonic and Hypersonic Technology Department, Linder H?he, Cologne, Germany, Email: johannes.riehmer@dlr.de;

    German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, Supersonic and Hypersonic Technology Department, Linder H?he, Cologne, Germany, Email: ali.guelhan@dlr.de;

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  • 正文语种 eng
  • 中图分类 航天（宇宙航行）;
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